Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(e71-il) E71 (5.15%) | Eppler E71 low Reynolds number airfoil Max thickness 5.2% at 25.7% chord Max camber 4.4% at 54% chord | Remove Airfoil details Airfoil plotter |
(e63-il) E63 (4.25%) | Eppler E63 low Reynolds number airfoil Max thickness 4.3% at 22.8% chord Max camber 5.3% at 50.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e71-il,e63-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e71-il | 50,000 | 9 | 48.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 50,000 | 5 | 49.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 100,000 | 9 | 75.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 100,000 | 5 | 74 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 200,000 | 9 | 108.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 200,000 | 5 | 103.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 500,000 | 9 | 162.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 500,000 | 5 | 143.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e71-il | 1,000,000 | 9 | 205 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e71-il | 1,000,000 | 5 | 139 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 50,000 | 9 | 52 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 50,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 100,000 | 9 | 77.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 100,000 | 5 | 77.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 200,000 | 9 | 112.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 200,000 | 5 | 110 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 500,000 | 9 | 176.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 500,000 | 5 | 160 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 9 | 235.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 5 | 157.7 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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